| タイトル | Trajectory Design for a Cislunar Cubesat Leveraging Dynamical Systems Techniques: The Lunar Icecube Mission |
| 本文（外部サイト） | http://hdl.handle.net/2060/20170001466 |
| 著者（英） | Howell, Kathleen C.; Bosanac, Natasha; Folta, David C.; Cox, Andrew |
| 著者所属（英） | NASA Goddard Space Flight Center |
| 発行日 | 2017-02-05 |
| 言語 | eng |
| 内容記述 | Lunar IceCube is a 6U CubeSat that is designed to detect and observe lunar volatiles from a highly inclined orbit. This spacecraft, equipped with a low-thrust engine, will be deployed from the upcoming Exploration Mission-1 vehicle in late 2018. However, significant uncertainty in the deployment conditions for secondary payloads impacts both the availability and geometry of transfers that deliver the spacecraft to the lunar vicinity. A framework that leverages dynamical systems techniques is applied to a recently updated set of deployment conditions and spacecraft parameter values for the Lunar IceCube mission, demonstrating the capability for rapid trajectory design. |
| NASA分類 | Astrodynamics |
| レポートNO | AAS 17-286
GSFC-E-DAA-TN38740-2 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
